JP7372179B2 - Components of broadband antenna systems in rotorcraft - Google Patents

Description

[0001] A rotorcraft, rotorcraft, or rotary-wing aircraft is a type of machine that flies through the air using lift generated by rotor blades. Examples of rotorcraft include, but are not limited to, helicopters, unmanned aerial vehicles (UAVs), small UAVs (sUAVs), unmanned aircraft systems (UASs and sUASs), and tilt-wing/tiltrotor aircraft. . Rotorcraft are used for military, commercial, and recreational purposes.

[0002] Rotorcraft have one or more central hubs and any number of rotor blades (typically 2 to 7) projecting from the hubs. Similar to conventional airplane wings, the blade shape is designed to provide lift when the blade rotates fully about a central hub. A rotorcraft may also be equipped with an antenna system for transmitting and/or receiving radio frequency ("RF") communications. These RF communications may be sent to or received from any number of different external targets, endpoints, wireless network nodes, or systems. As an example, some rotary aircraft have ground transmitters/receivers, other aircraft (e.g., airplanes, unmanned aerial vehicles ("UAVs"), other rotorcraft, launched weapons, etc.), and Some can also communicate with satellites in orbit above.

[0003] RF communications have advanced significantly in recent years. Now, more than ever before, rotorcraft can establish different RF communications links (often simultaneously) with external transmitters and receivers. These advances have greatly improved the safety of pilots, aircrews, and passengers, as well as the rotorcraft itself. Because of the benefits provided by RF communications, more and more RF components (eg, RF front-end components and RF back-end components) are being installed on rotorcraft. Increasing the number of RF components allows rotorcraft to establish more highly desired communication links, but at the potential cost of increased size, weight, and power.

[0004] The subject matter claimed herein is not limited to embodiments that overcome any disadvantages or operate only in environments such as those described above. This background is provided merely to illustrate one example of a technical field in which some of the embodiments described herein may be practiced.

[0005] Disclosed embodiments relate to antenna systems, communication systems, and methods for facilitating narrowband and/or wideband radio frequency (RF) communications by rotorcraft.

[0006] In some embodiments, an antenna system is integrated or provided within a rotorcraft, the rotorcraft having at least one central rotating hub and a plurality of rotor blades connected to the central rotating hub. including. The antenna system includes an RF front end and an RF back end. An RF front end includes multiple different RF components (e.g., antennas, amplifiers, mixers, tuners, waveguides, wires, etc.). The RF component forms part of at least one of the rotor blades of the rotorcraft (eg, by being embedded in the rotor blade). Additionally, at least some of these RF components are of different types (eg, antennas are different from amplifiers, amplifiers are different from mixers, etc.). Thus, the blade is improved because it includes multiple different types of RF components. The RF back end, on the other hand, is located elsewhere and is connected to the RF front end via a central rotating hub.

[0007] In some embodiments, a rotorcraft communication system includes an RF front end and an RF back end. The RF front end includes multiple antenna arrays and multiple amplifiers. Each antenna array includes multiple antenna elements, either of the same configuration or of varying configurations, to optimize performance. A first set of antenna elements and amplifiers is embedded in an inner portion of a first rotor blade of the rotorcraft. Similarly, a second set of antenna elements and amplifiers is embedded in the inner portion of the second rotor blade. (For example, some RF components are embedded within the blade, while other components are embedded conformally to the outer portion of the blade, such as antenna elements). The RF back end is connected to the RF front end via a central rotating hub. Additionally, the RF backend is configured to perform at least a conversion from digital signals to analog signals and vice versa.

[0008] Some embodiments relate to methods for simultaneously propagating multiple different RF signals to multiple different target endpoints. Initially, an RF backend provides multiple different signals simultaneously to all or different antenna arrays embedded in rotor blades of a rotorcraft. The antenna array is configured to steer beams emitted from the antenna array to corresponding different target endpoints. The plurality of different signals are converted from one or more intermediate frequencies (“IF”) to one or more radio frequencies at an RF back end or an RF front end. Each of the converted RF signals is then steered or directed to its corresponding target endpoint. In doing so, multiple different RF signals are simultaneously propagated to multiple different endpoints. Moreover, these RF signals are initially propagated from the rotor blades of the rotorcraft into three-dimensional space to a plurality of different targets. These operations take into consideration the need to meet FAA requirements.

[0009] This Summary is provided to provide a concise introduction to several concepts that are further described in the Detailed Description below. This Summary does not identify key or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.

[0010] Additional features and advantages are set forth in the description below, and some may be obvious from the description, or may be learned by practicing the teachings herein. The features and advantages of the invention may be realized and obtained by means of the instruments and combinations particularly pointed out in the appended claims. Features of the invention will be more fully apparent from the following description and appended claims, and may be learned by practicing the invention as described below.

[0011] In order to explain how the above-mentioned advantages and features and other advantages and features may be obtained, reference will now be made to specific embodiments illustrated in the accompanying drawings, and the subject matter briefly mentioned above will now be explained in more detail. do. BRIEF DESCRIPTION OF THE DRAWINGS Embodiments will now be described with further particularity and detail using the accompanying drawings, with the understanding that these drawings depict only typical embodiments and are therefore not intended to be limiting in scope.

FIG. 2 illustrates an example scenario in which a rotorcraft establishes an RF communications link with a ground-based receiver or transmitter. FIG. 2 is a diagram showing how electromagnetic waves include both electric and magnetic fields. FIG. 2 illustrates an example scenario in which a rotary-wing aircraft establishes multiple different RF communication links with multiple different receivers/transmitters, such as a ground dish dish, troops on the move, airplanes in flight, and satellites in space. . 1 illustrates a central rotating hub and rotor blade combination that enables rotorcraft flight; FIG. Demonstrates how different types of RF components (e.g., antennas, amplifiers, mixers, tuning systems, wires, waveguides, etc.) can be included as part of or embedded within the rotor blades. It is a diagram. 2 is a side profile view of an example rotor blade illustrating how different types of RF components may be embedded in the rotor blade; FIG. FIG. 3 also illustrates how at least some of the RF components can be shaped to match the shape of the rotor blade. FIG. 3 is a diagram illustrating a non-limiting example of a horizontal antenna pattern. FIG. 4 illustrates a non-limiting example of a vertical, or elevational, antenna pattern; FIG. 2 is a diagram illustrating an example of how an RF front end and an RF back end of an antenna system can be used to establish any number of wideband RF communication links. FIG. 2 is a diagram illustrating an example of how an RF front end and an RF back end of an antenna system can be used to establish any number of wideband RF communication links. FIG. 2 illustrates how RF components can be embedded in any rotor blade of a rotorcraft, even the tail rotor (eg of a helicopter). FIG. 2 illustrates how a rotorcraft can use its different hubs and rotors to establish simultaneous broadband RF communication links with any number of different external receivers or transmitters. 1 is a flow diagram of an example method for simultaneously propagating multiple different RF signals to multiple different target endpoints, where the signals are initially propagated in three-dimensional space from a rotor blade of a rotorcraft. 1 is a flow diagram of an example method for simultaneously propagating multiple different RF signals to multiple different target endpoints, where the signals are initially propagated in three-dimensional space from a rotor blade of a rotorcraft. 1 illustrates an example computer system that can be used to perform any of the disclosed operations and that can be used to control the disclosed antenna/communications system. FIG.

[0024] The disclosed embodiments relate to antenna systems, communication systems, and methods for facilitating narrowband and/or wideband radio frequency (RF) communications in rotorcraft. The disclosed embodiments are operable in accordance with any US government standards, including DoD and FAA requirements, any commercial use, and/or any other official use.

[0025] In some embodiments, the RF front end of the antenna system is included as part of at least one rotor blade of a rotorcraft. Since the front end includes different types of RF components, the rotor blades also include different types of RF components. The RF back end, on the other hand, is located elsewhere and is connected to the RF front end via the central rotating hub of the rotorcraft.

[0026] In some embodiments, an RF front end of a communication system includes multiple antenna arrays (each array including one or more antenna elements) and multiple amplifiers. A first set of antenna elements and amplifiers is embedded inside a first rotor blade of the rotorcraft, and a second set of antenna elements and amplifiers is embedded inside a second rotor blade of the rotorcraft. The RF back end of the communication system is connected to the RF front end via the rotorcraft's central rotating hub. The RF backend is configured to at least convert digital signals to analog signals and vice versa.

[0027] In some embodiments, a method is provided for simultaneously propagating multiple different RF signals to multiple different target endpoints. In doing so, the RF backend simultaneously provides multiple different signals to different (or all) antenna arrays embedded in different rotor blades and forming part of the RF front end. These different signals are also converted from intermediate frequency to radio frequency at the RF backend or RF frontend. Each (or all) of the different antenna arrays then directs its corresponding converted RF signal to a corresponding target endpoint, such that multiple different RF signals propagate to multiple different target endpoints simultaneously. I will do it.

technical effect
[0028] One of the issues facing aircraft and RF system designers is aircraft real estate (i.e., adequate surface area for the antenna aperture and proper aperture separation to reduce or eliminate local interference). is limited. In fact, rotorcraft are now packed with so many different types of hardware (including RF communication systems) that space for additional hardware is running out. Despite these shortfalls, and despite limited space for area and hardware, it has become increasingly important to provide as many RF communication links as possible. Therefore, there is a great need to improve the way RF communication systems are designed to support the ever-increasing demand for providing more RF communication links to rotorcraft.

[0029] Yet another problem facing designers is how to eliminate or reduce RF communication interruptions that occur when RF communications occur in rotorcraft. Specifically, conventional RF systems in rotorcraft have faced major signal interference as a result of rotor blades spinning overhead, as well as interference from other parts of the aircraft fuselage. Several techniques have been developed to address these interferences (e.g. by pulsing/bursting RF signals when the blade is not directly above the RF antenna), but these techniques This may result in increased or suboptimal results (e.g., bursting the signal may result in data loss or further loss of efficiency). Therefore, there is also a great need to improve how RF communications are transmitted and received, especially in rotorcraft.

[0030] Use of the disclosed embodiments can provide solutions to these problems. For example, by embedding different types of RF components into rotor blades of rotorcraft, the disclosed embodiments take advantage of hitherto unclaimed and unexploited real estate. This provides a significant improvement. In doing so, the disclosed embodiments can significantly increase the number of RF communication links that an aircraft can establish.

[0031] As previously mentioned, the amount of real estate in rotorcraft is quite limited. Furthermore, it is highly desirable to increase the number of communication links. Given that real estate is limited, the disclosed embodiments take advantage of the available real estate, namely the aircraft's rotor blades. Until now, rotor blades have been an untapped resource for broadband RF communications, but disclosed embodiments provide much-needed technological improvements by utilizing rotor blades in a unique and highly advantageous manner. provide.

[0032] By placing RF components high above the fuselage (e.g., within the rotor blades), the disclosed embodiments significantly eliminate overhead interference that previously impeded upward RF communications ( or completely eliminate). In this regard, overhead RF communications may be improved. Additionally, the disclosed embodiments may allow transmission to occur continuously rather than periodically.

[0033] The disclosed embodiments also improve upon the technology by significantly increasing the number of RF components (and therefore also the number of links) while providing virtually zero net weight increase for rotorcraft. That is, by manufacturing rotor blades in accordance with the disclosed techniques (e.g., embedding RF components within the rotor blades), the present embodiments significantly increase the number of RF components in an aircraft while substantially reducing the weight increase. set to zero. In other words, the weight added by the new RF component is reduced by removing material from the rotor blade (eg, to make room for the RF component). Thus, the disclosed embodiments provide an important and significant improvement to rotorcraft antenna systems by increasing the number of additional links from one platform.

RF communication link
[0034] Turning now to FIG. 1, this is a diagram illustrating an example environment 100 in which a rotorcraft 105 and a ground transmitter/receiver 110 have established an RF communications link 115 with each other. The RF communications link 115 allows the rotorcraft 105 and the ground transmitter/receiver 110 to communicate and exchange information (e.g., transmit and reception) possible.

[0035] According to the disclosed embodiments, rotorcraft 105 can transmit and receive data packets of any type. For example, in some situations, data packets 120A-C include low band audio data, high band video data, or any other type of wideband data or signal. Accordingly, rotorcraft 105 is capable of transmitting and/or receiving any type of broadband RF communications.

[0036] To establish the RF communications link 115, the rotorcraft 105 transmits or receives electromagnetic waves to a ground transmitter/receiver 110. FIG. 2 is a diagram illustrating an example electromagnetic wave 200, representing both narrowband and wideband signals. Electromagnetic wave 200 includes an electric field 205 and a magnetic field 210. The electromagnetic waves 200 may be emitted by an antenna, or may be intercepted, or more precisely received, by the antenna.

[0037] FIG. 3 is a diagram illustrating another example environment 300, which is somewhat similar to environment 100 of FIG. However, in environment 300, a rotorcraft 305 representing rotorcraft 105 of FIG. 1 uses its RF components (e.g., antennas, amplifiers, mixers, tuning mechanisms, waveguides, wires, etc.) Establishing multiple RF communication links with external entities simultaneously.

[0038] As shown, rotorcraft 305 is currently in communication with orbiting satellite 310 via RF communications link 315. Rotorcraft 305 is also currently in communication with aircraft 320 via RF communications link 325 . Finally, rotorcraft 305 is also currently in communication with ground parabolic antenna 330 via RF communication link 335 and with ground forces 340 (stationary or moving) via RF communication link 345. Ground forces 340 should be broadly construed to include moving or stationary troops and/or vehicles. Rotorcraft 305 can establish any number of RF communication links, only limited based on the number of available RF components.

rotorcraft
[0039] FIG. 4 is a diagram illustrating a rotorcraft 400 representing rotorcraft 305 of FIG. Here, an enlarged view 405 of the central rotating hub 410 and rotor blades 415 and 420 of the rotorcraft 400 is shown. Rotor blades 415 and 420 are each connected to a central rotating hub 410 that is attached to a drive shaft (not shown). The drive shaft is attached to a transmission (not shown), which is attached to the rotorcraft engine. Although only two rotor blades 415 and 420 are shown, rotorcraft 400 may include any number of rotor blades, typically between two and seven.

[0040] As shown by arrow 425, rotor blades 415 and 420 rotate/spin about central rotating hub 410. The rotation speed can be any speed, but approximately 200 Hz is a typical speed. Arrows 430A and 430B show how central rotating hub 410 can adjust the angle of inclination of blades 415 and 420. That is, flight control of rotorcraft 400 is based on tilting rotor blades 415 and 420 back and forth.

[0041] Although rotorcraft 400 is in the form of a helicopter, the disclosed embodiments may be implemented in any rotorcraft (eg, drone, tilt-wing, etc.). Most helicopters have a fuselage, a tail boom, a main rotor, and a tail rotor. A tail rotor is provided to offset rotational torque resulting from rotation of the main rotor. As outlined above, a helicopter's fuselage and tail boom are often located under the shadow of the rotor blades.

[0042] In conventional helicopters, the antenna system is often located above or below the fuselage or tail boom, and the antenna system includes both an RF front end and an RF back end. Depending on the number and size of the blades, at a given point the blades spinning overhead will block or otherwise impede these antenna systems. That is, such configurations often cause RF link interruptions each time a rotor blade passes over the antenna. Therefore, conventional helicopter antenna systems must send RF signals through the shadow of the rotor blades, which often results in the problems described above.

Embedded RF components
[0043] To solve some of the problems of the prior art, disclosed embodiments place at least some of the antenna systems on the rotor blade itself. In doing so, the problem of compensating for rotor blade shadows can be completely eliminated (for upward RF communications). Furthermore, since it involves the use of previously untapped real estate, the problem of limited real estate is alleviated.

[0044] Accordingly, FIG. 5 depicts an example rotor blade 500, which is representative of rotor blades 415 and 420 of FIG. Although only one rotor blade is shown in some figures, the principles disclosed apply to one, several, or all rotor blades.

[0045] According to the disclosed embodiments, rotor blade 500 is used herein as part of an antenna system that facilitates broadband radio frequency (RF) communications in a rotorcraft. Here, the antenna system includes an RF front end 505 that includes any number of RF components, such as RF component 510, RF component 515, RF component 520, and RF component 525. Although there are only four RF components labeled and only 18 RF components shown in FIG. 5, any number of RF components can be included as part of the RF front end 505; However, there are limitations only on the size or dimensions of rotor blade 500 and the number of rotor blades available. Additionally, the RF components shown in the drawings are not necessarily to scale. The components may be larger or smaller than shown, have different relative dimensions and/or shapes, and may have different arrangements.

[0046] These RF components (e.g., RF components 510, 515, 520, and 525) are configured to transmit and/or receive any number of broadband RF communications as electromagnetic waves into three-dimensional space (e.g., broadband electromagnetic waves 200) in FIG. Examples of RF components also include, but are not limited to, antenna arrays (e.g., each array includes one or more antenna elements), RF amplifiers, mixers, waveguides, wires, and frequency tuning mechanisms. It's not a thing. As shown in FIG. 5, the RF component actually forms part of a rotor blade 500. That is, the RF components are actually embedded in the inner portion of rotor blade 500 so that they are not exposed to the external environment. The RF components are shown as dotted lines to symbolically represent how they are embedded within the rotor blade 500. A technical example of how to embed an RF component inside rotor blade 500 will be described later. In some embodiments, at least some RF components (eg, antenna elements) are disposed conformally (ie, coplanar) with an outer portion of rotor blade 500. More precisely, a portion of the RF component is embedded within the rotor blade 500, while another portion is located in the same plane as the outer shape of the rotor blade 500. As an example, consider an antenna element (eg, a radome). In order to emit a signal, the propagation path of the antenna element should be free of obstacles. Therefore, the signal emitting portion of the antenna element may be arranged horizontally, that is, on the same plane as the outer surface shape of rotor blade 500. In this way, the rotor blade 500 will not interfere with the signal. The remainder of this antenna element (if any) may be embedded in rotor blade 500. Therefore, some RF components may be fully embedded within the rotor blade 500, while other RF components may only be partially embedded, with portions molded to conform to the external shape of the rotor blade 500. good. In such cases, an RF transparent paint or material (eg, some type of low-loss coating) may be placed over the conformally shaped part to protect it from the external environment.

[0047] At least some of the RF components within rotor blade 500 are of different types. For example, RF component 510 may be an antenna array, RF component 515 may be an RF amplifier, RF component 520 may be a mixer, and RF component 525 may be a frequency tuning mechanism. Additionally or alternatively, RF components 510, 515, 520, and 525 may be an integrated antenna RF front end. The antenna elements may vary in size, spacing, or taper. Other RF components may be additional antenna arrays, amplifiers, mixers, tuning mechanisms, and/or wires or waveguides connecting different RF components. In this regard, the rotor blade 500 has a vast supply/control network completely embedded within its own internal region. One advantage of antenna arrays is that even if a portion of the array fails for any reason, the array remains operational and can emit or receive signals. Therefore, this embodiment makes advantageous use of an antenna array.

[0048] The antenna system also includes an RF back end 530, which is connected to the RF front end 505 via a central rotating hub 535, which is representative of central rotating hub 410 in FIG. If a mixer is included as part of the RF front end 505, the RF back end 530 provides for converting analog intermediate frequency (“IF”) signals into digital signals that can be used by the computer system, and vice versa. It is being If the RF mixer is included as part of the RF back end 530, the RF back end 530 converts the RF signal to an IF signal and then converts the analog IF signal into a digital signal for signal processing by a computer system. (and vice versa). Accordingly, RF backend 530 may include any number of digital-to-analog converters ("DACs"), analog-to-digital converters ("ADCs"), tuning mechanisms, mixers, etc. to generate or process digital and analog signals. , an amplifier, and a computer system.

[0049] The disclosed embodiment communicatively couples the RF front end 505 to the RF back end 530 via a central rotation hub 535. That is, physical wiring (and/or slip ring configuration) extends from the RF backend 530 to the inner ring of the central rotating hub 535. Central rotating hub 535 also includes an outer ring connected to a rotor blade (eg, rotor blade 500), where the outer ring is communicatively coupled to an RF component of the blade. A brush is provided within the central rotating hub 535 to connect the inner and outer rings to each other. As a result, RF back end 530 is seamlessly coupled to RF front end 505.

[0050] FIG. 6 is a side profile view of an example rotor blade 600 that is representative of rotor blade 500 of FIG. Similar to the structure of rotor blade 500, an RF front end 605 is embedded within rotor blade 600. Additionally, rotor blade 600 can include any number of RF components, including RF components 610, 615, 620, 625, 630, 635, 640, 645, 650, 655A, 655B, 660, 665, and 670, etc. However, it is not limited to these. Again, different types of RF components are embedded in the inner portion of rotor blade 600. RF components are not necessarily to scale. Additionally, in some embodiments, the blade 600 may be embedded with an RF component by placing the RF component on the surface of the blade and then conformally coating the blade to encapsulate the RF component. The different types include: (1) one or more antenna arrays (e.g., each array includes one or more corresponding antenna elements configured to propagate electromagnetic signals); (2) received signals; (3) one or more mixers configured to convert the RF signal to an intermediate frequency (IF) signal and convert the IF signal to an RF signal; (4) one or more waveguides, (5) one or more wires, or (6) one or more tuners.

[0051] In some embodiments, rotor blade 600 includes only one type of antenna array, and in other embodiments, rotor blade 600 includes multiple different types of antenna arrays. Examples of array types include tapered Vivaldi antenna arrays, fractal antennas, staggered patch antenna arrays, or linear circular polarization (CP) antenna arrays. antenna arrays). Briefly, a Vivaldi antenna array is a type of tapered slot antenna that includes coplanar broadband elements. A staggered patch antenna array is a type of low-profile antenna that can be mounted on a relatively flat surface. A linearly circularly polarized antenna array generates a linearly polarized signal that travels through three-dimensional space while vibrating horizontally or vertically in a specific plane.

[0052] In some embodiments, multiple RF components may be stacked inside rotor blade 600. For example, RF component 655A is shown superimposed on RF component 655B. In some embodiments, the RF component may be shaped to match the overall shape of rotor blade 600. For example, RF component 625 is shown flexing to generally follow the curvature of rotor blade 600.

[0053] FIG. 6 shows that the first set of RF components (e.g., RF components 610, 615, 620, 625, and 630) are physically located near/near the top surface (i.e., the back surface) of the blade 600. It also shows that A second set of RF components (e.g., RF components 635, 640, 645, 650, 655B, 660, 665, and 670) are physically located near/near the lower surface (i.e., ventral surface) of the blade 600; The ventral surface is the opposite surface from the dorsal surface. RF components 610 and 615 are specifically positioned flush (ie, conformally) with the outer portion of rotor blade 600. Here, an RF transparent coating may be placed over the RF components 610 and 615 to act as a protective membrane. In some embodiments, RF components 610 and 615 are antenna elements positioned to match the external shape of rotor blade 600 so that they can emit signals without interference from rotor blade 600. . In some embodiments, the first set of RF components is controlled simultaneously with and independently of the second set of RF components, as described in more detail below. In one example, a first set of RF components transmits a first electromagnetic wave in an upward direction toward the rotorcraft, while a second set of RF components simultaneously transmits a first electromagnetic wave in a downward direction toward the rotorcraft. It is possible to send 2 electromagnetic waves. As can be seen in FIG. 6, the front end 605 of the antenna system may include any type of active and/or passive circuitry and other hardware used to transmit and receive signals. In some embodiments, the RF components embedded in the rotor blades 600 may be honeycombed to protect the RF components from vibrations and other disturbances. A shock absorbing gel may be included within rotor blade 600 to absorb shock, where the shock absorbing gel at least partially envelops the RF component.

[0054] Additional RF links can be created from one platform by embedding RF components into the rotor blades. Furthermore, by embedding the RF components within the rotor blade 600, the RF components do not interfere with the aerodynamic performance of the rotor blade 600.

[0055] Techniques for embedding RF components within rotor blades 600 are disclosed herein. First, rotor blades (eg, rotor blade 600) are now typically made of composite materials. Examples of materials include, but are not limited to, aluminum, carbon fiber, Kevlar, fiberglass, or any other type of composite material. The rotor blade also includes a central core. From this central core, a conventional blade is gradually built up in layers until the blade is fully formed.

[0056] According to the disclosed technology, when a new layer is added to the core, the new layer is a compartment, chamber, space, recessed area, or other shape that It is shaped to create a shape that matches, or more precisely will accommodate, the particular RF component selected for placement in the location. In this way, the inner portion of the rotor blade is gradually shaped to accommodate different RF components. These molding processes allow RF components to be embedded inside the rotor blade during manufacture of the rotor blade. That is, since the rotor blade is a closed object, the RF components are embedded inside the rotor blade during the lamination process.

[0057] Thus, any type of RF components including antenna elements/arrays, amplifiers, mixers, tuners, wires, and waveguides may be added, specifically embedded, to the rotor blade during manufacture of the rotor blade. . Such a process produces a rotor blade that appears unchanged from the outside (ie, the appearance of the rotor blade is substantially unchanged) but is actually improved due to the embedded RF components.

[0058] In some embodiments, two, three, four, or any number of RF components may be stacked, as shown in RF components 655A and 655B of FIG. Stacking in this manner can improve performance in achieving very wideband signals. Additionally and/or alternatively, some of the RF components may be tapered to mitigate any type of satellite interference in the sidelobes of the antenna radiation pattern, as described in more detail below.

[0059] For antenna arrays embedded in rotor blades 600, any type of desired antenna aperture may be achieved. That is, the antenna elements can be arranged/placed within the inner portion of the rotor blade to achieve performance comparable to any type of antenna aperture (including typical non-arrayed configurations). Such an arrangement allows for careful aiming, steering, directing, or tracking of the beam of each antenna array, or even the beam of each antenna element, as described in more detail below. The aim also takes into account the rotation of the blade (more on this later).

[0060] The embedded RF component may include a very low profile antenna array that can be conformal to fit inside a rotor blade of any size. The RF components may also include amplifiers that provide sufficient RF power and are physically robust to survive being embedded in a rotating rotor blade. Even the antenna receiver's low noise amplifier ("LNA") can be embedded in the rotor blade.

[0061] Accordingly, amplifiers may be placed in close proximity to the antenna array to achieve improved signal-to-noise ratio ("SNR"). The embedded RF components may also include any type of tuning mechanism to match the impedance and any type of mixer to perform RF to IF and IF to RF conversion. Therefore, RF/IF conversion or IF/RF conversion may be performed directly within the rotor blade. Alternatively, the RF/IF or IF/RF conversion can be performed external to the rotor blades, if desired. In some embodiments, where the RF/IF or IF/RF conversion is performed depends on the functionality and characteristics of the central rotating hub connection and whether the connection introduces excessive losses or noise. Dependent.

Antenna pattern example
[0062] Reference is now made to FIGS. 7A and 7B. These figures show some non-limiting examples of antenna radiation patterns. These patterns are shown for illustrative purposes only and should not be considered limiting or limiting in any way. In a later section, we will explain how to electronically steer the antenna array's beam in order to lock it onto an external transmitter or receiver.

[0063] FIG. 7A shows an antenna range graph 700A showing an example horizontal pattern 705. That is, a rotor blade of a rotorcraft is assumed to include the disclosed RF component. When viewed from above (i.e., a top-down view as shown in azimuth 705A), the antenna array embedded in the rotor blade of the aircraft emits an electromagnetic field and then azimuthal as shown in example horizontal pattern 705. It can emit a radiation pattern.

[0064] Similarly, FIG. 7B shows a related antenna range graph 700B, which is from an elevation view (ie, viewed horizontally from the side to the rotorcraft). FIG. 7B is an example upwardly radiating vertical pattern (steerable) 710A and a downwardly radiating vertical pattern (steerable) 710B. The disclosed embodiments have a first set of RF components embedded near the back surface of the rotor blade and a second set of RF components embedded near the ventral surface of the rotor blade. , 5, 6, 7 (or any number) separate, steerable antenna patterns.

[0065] That is, the first set can aim upward, and the second set can aim downward. As will be detailed later, the antenna elements included in the first set can function as one antenna unit by all operating uniformly, or by each operating independently. , can also function as a number of antenna units. Such diversity allows for an increase in the number of RF communication links that can be formed. Similar techniques can be used for the second set of RF components.

[0066] As an example, consider a scenario in which a rotor blade includes eight antenna elements located on or in its back surface and another eight antenna elements located on or in its ventral surface. . Here, all eight antenna elements on the upper part may function as one antenna unit by performing the same operation at the same time. Similarly, the bottom eight antenna elements may all perform the same operation in unison. In a situation where the top eight antenna elements operate in unison with each other and the eight bottom antenna elements operate in unison with each other, only two RF communication links are formed. A large number of antenna elements working together allows for multiple RF communications (both narrowband and wideband). In other situations, all 16 antenna elements may operate independently of each other to form 16 potential RF communication links.

[0067] Also shown in FIG. 7B is a main lobe 715 and an example sidelobe 720, where orientation 725 indicates that the orientation is positioned as viewed from the side. As discussed below, the disclosed embodiments are useful for all types of low probability of detection ("LPD") maneuvers, low probability of interception ("LPI") maneuvers, anti-jamming, satellite interference, and geo-steering (geo-steering). steering) can also be performed. Such steering techniques adjust the width and strength of the main lobe 715 and side lobes 720. Arrow 730 shows how the lobe can be steered.

[0068] The disclosed embodiments provide a highly diverse antenna architecture so that multiple different frequency bands (ie, wideband) can be supported. In other words, multiband RF communication can be performed. Some examples of supported frequency bands/widths include L-band, S-band, C-band, X-band, Ku-band, K-band, Ka-band, or bands above 40GHz up to 90GHz; It is not limited. In this regard, disclosed embodiments are operable at frequencies between at least 500 MHz and 90 GHz. For reference, the L band includes wavelengths with frequencies between 1 and 2 GHz. The S-band includes wavelengths with frequencies between 2 and 4 GHz. The C band includes wavelengths with frequencies between 4 and 8 GHz. The X-band includes wavelengths with frequencies between 8 and 12 GHz. The Ku band includes wavelengths with frequencies between 12 and 18 GHz. The K-band includes wavelengths with frequencies between 18 and 27 GHz. The Ka band includes wavelengths with frequencies between 27 and 40 GHz.

electronic steering
[0069] As outlined above, the disclosed embodiments can electronically "steer" or "target" any of the various combinations of antenna elements embedded in the rotor blades. As an example, a helicopter has four rotor blades, each blade having 16 top antenna elements and 16 bottom antenna elements, so that the helicopter has additional Let's say we have 128 antenna elements (eg 16x2x4). Each antenna element can be electrically biased independently of the other antenna elements, or each antenna element can be electrically biased independently of the other antenna elements, or each antenna element can be It can also be operated as an antenna array in coordination with any number of other antenna elements. To improve array performance (eg, increased gain, more precise beam steering, etc.), a rotor blade antenna element may also operate in conjunction with another rotor blade antenna element. Note that the beam is steered using multiple antenna elements. Additionally, as discussed below, a single rotor blade can be configured to support multiple RF links. The disclosed embodiments are also operable to support waveform generation and modem functionality.

[0070] As an example, the 16 upper antenna elements of a rotor blade can operate in conjunction with the 16 upper antenna elements of other rotor blades. In some situations, all 64 upper antenna elements operate in unison with each other, thereby providing the opportunity to establish multiple RF communication links (both narrowband and wideband) while reducing antenna efficiency. It is also possible to increase the antenna gain. Thus, a robust network is provided for steering any number or combination of antenna elements on a rotor blade.

[0071] Individual antenna elements or forming small clusters or groups of antenna elements may be used for command and control ("C2") type communications. This is because such communications require relatively low bandwidth. To achieve higher bandwidth communications (eg, video data), multiple antenna elements may be merged or combined to perform the same operation in unison. Such a combination can create a large antenna aperture, which also increases antenna efficiency and antenna gain. This increased efficiency and gain makes it possible to transmit and receive high-bandwidth signals (eg, video). As a result, greater gain and efficiency measurements can be obtained through the larger area aperture by combining the antenna elements to perform the same operation in unison.

[0072] Therefore, the aperture of the antenna can be dynamically adjusted in real time and as needed. In particular, the disclosed embodiments can account for the "equivalent isotropic radiated power" ("EIRP") of an antenna system, where EIRP is the transmitter power of the antenna and the isotropic antenna of the transmitter. EIRP is the product of the antenna's gain (in a given direction).This EIRP can be used to move the aperture to ensure that the propagating signal correctly reaches the endpoint (e.g., satellite, airplane, etc.). Additionally, EIRP can be adjusted by the signal-to-noise ratio or gain-to-noise-temperature ratio (G/T) (e.g., where "G" is the antenna gain in decibels and received frequency, and "T" is the Kelvin can be used to ensure that the equivalent noise temperature of the receiving system, denoted by , is adequate. Therefore, the aperture can be adjusted to have the desired gain to fit the entire RF link, thus allowing the link to be established/closed. Therefore, a desired gain may be achieved, and the gain can be changed by dynamically adjusting the aperture.

[0073] To electronically steer the antenna elements, the RF back end changes the phase and amplitude of the signal sent to the RF front end, and in some cases applies geospatial adaptive processing schemes. That is, the antenna system has a feed network that can feed signals to the RF front end for propagating the signals to external entities.

[0074] Various techniques are available for electronically steering/aiming the beam. These techniques generally modify the phase and amplitude of the signal sent to the RF front end. The first technology is "MIMO" (multiple-input and multiple-output) technology. MIMO is a method of increasing the capacity of an RF link through the use of multiple transmit/receive antennas, thereby exploiting multipath propagation. That is, when interference occurs as a result of using a large number of different antenna arrays, MIMO can address the problem by performing multipath from different apertures. In this regard, any number of signals can be transmitted or received simultaneously from each other on the same RF frequency/channel.

[0075] Another technique for aiming antenna arrays/elements is referred to as "OAM" (orbital angular momentum multiplexing). OAM is a physical layer technology in which signals are multiplexed together over an electromagnetic wave, generally meaning that this multiplexing occurs through the use of the orbital angular momentum of the electromagnetic wave. Such a process allows this electromagnetic wave to be distinguished from different orthogonal signals. In this regard, OAMs typically rely on electron spin (of arbitrary scale) to steer the antenna. Since the RF components are embedded in the rotor blades and the rotor blades rotate, OAM uses the rotating rotor blades as well as the rotating electrons to focus the electromagnetic waves to specific endpoints. be able to. OAM also increases diversity in signaling. Furthermore, since the signals can be orthogonal to each other, their interference with each other is reduced (or even non-existent). As a result, it is possible to stack many different channels into one electromagnetic wave simultaneously, thereby achieving many different links from the same electromagnetic signal/waveform.

[0076] These maneuvering techniques and any other maneuvering techniques allow the disclosed embodiments to increase the link diversity available in an antenna network. "Link diversity" generally means that many RF communication links of various types may be established, these links may span different bands/frequencies, and may be generated simultaneously with each other. Diversity is also commonly associated with spatial diversity, polarization diversity, and frequency diversity.

[0077] These techniques also take into account the rotational speed of the rotor blades, since the antenna elements can be placed on the rotating rotor blades. That is, an n-dimensional moving body analysis/model may be performed to compensate for the rotational speed of the rotor blade. Because each element is itself a moving object, and/or the elements can behave in unison with each other, the antenna system requires an n-dimensional moving object analysis that correlates to how the antenna elements are configured. / model can be constructed.

[0078] Using this n-dimensional moving object model, the phase and amplitude of the signal can be determined as a function of the rotation of the rotor blade. In some embodiments, each portion of the electromagnetic wave/beam (eg, from each array element) is electronically steered to an external endpoint. This steering occurs each frame as the antenna elements move around the central rotating hub, so that by the time the signal reaches the endpoint, it is a complete set of composite data/information. Dynamically adjusting the signal in this way (e.g. by changing phase and amplitude) is "rotational compensation" and can be performed for any number of antenna elements embedded in any number of rotor blades. .

[0079] Performing rotational compensation allows the antenna system to aim its electromagnetic beam to track any desired target. Additionally, the resulting beam can be shaped to have similar characteristics to conventional beams. Thus, the receiver can operate without any modification or need to know that the transmitted signal was sent using the improved techniques described herein. In this regard, embodiments are receiver and transmitter independent.

[0080] These improved electronic steering techniques allow antenna systems to perform low detectability (LPD), low interference/interceptability (LPI), anti-jamming, satellite interference, geolocation, even at wideband frequencies. , cosite interference, position-navigation-timing (PNP), and geosteering (and other operations can be performed at narrowband frequencies). Therefore, when the disclosed embodiments are implemented on a military rotorcraft, electronic warfare ("EW") may be waged. Briefly with respect to LPD and other EW steering techniques, sidelobes of the antenna pattern (e.g., sidelobes 720 in FIG. 7B) can be adjusted to suppress the gain in those regions (e.g., by using tapered antenna arrays). )be able to. Since side lobes can be controlled by such an operation, it becomes possible to know who sees the signal and who does not see it. Additionally or alternatively, embodiments may be configured to shape the signal to maintain a constant spectral flux density. Spectral flux density defines the amount of power per area at a given physical location. Embodiments can shape the signal to limit the power sent to a given physical location, limit the spectral flux density, and ensure that the signal provides LPD, LPI, geolocation, PNT, etc. It can be so.

[0081] In some situations, the tips of the rotor blades may actually flutter to some extent (eg, due to turbulence). Rotor blades are typically made of plastic material and can bend slightly up or down depending on speed. The disclosed maneuvering techniques can identify when such bending occurs (e.g., when the link strength increases or decreases, or when a link is momentarily severed as a result of a flapping change in target position). (as the case may be), corrective action can be taken to realign the electromagnetic waves to the target endpoint. Such corrective actions can be taken very quickly (eg, in a few nanoseconds), thereby preserving the strength of the link. As an example, suppose a pilot is communicating with an endpoint using an antenna system. If the rotor blades flutter or buckle for any reason and the link momentarily goes out of focus, this maneuver allows immediate corrective action to be taken so the pilot (or certain communication components) knows that the link was out of focus. You won't even notice it. As a result, via electronic steering, the antenna array can "bounce" back to its original location almost instantly. In this regard, the disclosed embodiments provide error correction and any type of compression or compensation to keep the RF communication link as strong as possible during electronic maneuvering. can be guaranteed.

Multiple simultaneous communication links
[0082] Figures 8A and 8B illustrate several situations in which multiple instant broadband RF links are established. In FIG. 8A, a rotorcraft 800 has an RF front end 805A on one rotor blade, an RF front end 805B on another rotor blade, and an RF front end 805C on yet another rotor blade. This is shown as including the tail rotor blade). RF front ends 805A, 805B, and 805C represent any of the RF front ends described above in that they may include any number of RF components.

[0083] In this situation, RF front ends 805A, 805B, and 805C include multiple antenna arrays and multiple amplifiers, as shown in previous figures. Each antenna array includes multiple antenna elements. Further, the RF front end 805A includes a first set of antenna elements and amplifiers, which set is embedded in the inner portion of the corresponding rotor blade, and the RF front end 805B includes a second set of antenna elements and amplifiers. a set, which is also embedded in the inner portion of the corresponding rotor blade. RF front end 805C will also have its own RF components.

[0084] Rotorcraft 800 also includes a first rotating hub 810A, a second rotating hub 810B, and an RF back end 810. RF front ends 805A and 805B are connected to RF back end 810 via a first rotating hub 810A, and RF front end 805C is connected to RF back end 810 via a second rotating hub 810B. RF backend 810 converts digital signals to analog signals and/or converts analog signals to digital signals. Accordingly, rotorcraft 800 is equipped with an antenna/communications system that facilitates instantaneous mixed broadband RF communications.

[0085] In the scenario shown in FIG. 8A, the RF front end 805B has established at least two separate RF communication links, and the RF communication links are directed to two separate target endpoints. To illustrate, the communication system is currently communicating with endpoint 815 and endpoint 820. Embodiments can dynamically form any number of different arrays within each of RF front ends 805A, 805B, and 805C. These antenna array beams can also be directed to different locations/endpoints by electronically steering the beams emitted from the antenna array.

[0086] In some embodiments, the process of dynamically forming different antenna apertures and steering these apertures may be based on RF front end availability and/or antenna element availability. be. For example, because endpoint 815 is located slightly above the front of rotorcraft 800, a forward and upwardly facing antenna element or array may be used to establish an RF communications link with endpoint 815. Similarly, since endpoint 820 is located slightly below the front of rotorcraft 800, a forward and downward facing antenna element or array may be used to establish an RF communications link with endpoint 820.

[0087] In addition to electronically steering antenna elements to endpoints and performing EW functions (e.g., satellite interference, LPD, LPI, etc.), antenna systems also provide pilot safety protection when electronically steering radiated energy. It can also be configured to take into account. For example, the disclosed embodiments can generate or otherwise obtain mapping of rotorcraft. Based on this mapping, and based on the rotational speed and position of the rotor blades, the antenna system is configured to avoid radiating energy downward when the rotor antenna is directed toward the pilot or into the crew compartment. can do. If desired, other parts of the rotorcraft can be avoided during energy release. It is also possible to control the antenna system to compensate for movements of the rotorcraft, such as, for example, tilting movements, banking movements, or any other type of movement. Therefore, the electromagnetic energy emitted by the antenna system can be managed in a highly directional manner.

[0088] FIG. 8B illustrates a scenario in which different antenna elements are dynamically combined with other elements to form various apertures for establishing an RF communication link. Specifically, FIG. 8B shows an RF front end 825 and an RF back end 830 having multiple different RF components. RF front end 825, RF component, and RF back end 830 represent the front end, RF component, and RF back end described above.

[0089] Here, the RF components are dynamically separated into four different groups, specifically arrays, such as array 825A, array 825B, array 825C, and array 825D. In FIG. 8B, which RF component belongs to which array is indicated by different shading. For example, array 825A is shown as including four antenna elements, array 825B is shown as including only one antenna element, array 825C is shown as including only one antenna element, and array 825D is shown as including only one antenna element. is shown as containing eight antenna elements. Of course, any number or combination of antenna elements may be used, and each antenna element may be independently biased (eg, in other scenarios where groups of arrays are not formed). Thus, in some embodiments, each element is independently operable as an independent antenna unit. In some cases, groups of antenna elements (or even all of the elements) may be collectively controllable via electronic antenna steering such that multiple antenna elements can collectively operate as one antenna unit. be.

[0090] Here, array 825A has established an RF communication link with endpoint 835. Array 825B has established an RF communications link with endpoint 840. Array 825C has established an RF communications link with endpoint 845. Finally, array 825D has established an RF communications link with endpoint 850. Accordingly, any number of RF communication links may be established with any number of target endpoints.

[0091] FIG. 9 depicts a scenario that includes a rotorcraft 900 with a secondary rotor hub/blade 905 and another rotorcraft 910. Here, rotorcraft 900 has established an RF communications link 915 using RF components embedded in secondary rotor hub/blade 905 .

[0092] FIG. 10 depicts another scenario in which a rotorcraft 1000, including a main rotor 1005 and a secondary rotor 1010, is in communication with another aircraft. In particular, RF components within main rotor 1005 are used to communicate with aircraft 1015 via RF communications link 1020. Simultaneously with the establishment of RF communications link 1020, RF components within secondary rotor 1010 are being used to communicate with aircraft 1025 via RF communications link 1030. The system may also communicate with individuals, vehicles, or other entities on the ground, which may be stationary or moving, as illustrated in communication with person 1035 in FIG. Thus, by embedding RF components into rotor blades of rotorcraft, the number and diversity of RF communication links, even air-to-ground links, can be greatly expanded and improved.

Method example
[0093] Turn now to FIGS. 11A and 11B, which illustrate a number of methods and method acts that may be performed. Method acts may be listed in a certain order or shown in a flow diagram as occurring in a particular order, except when specifically referenced or when one act is completed before another act is performed. They do not need to be in a particular order unless a dependency requires it.

[0094] FIG. 11A is a flow diagram of an example method 1100 for controlling an antenna system that includes an RF front end and an RF back end of a rotorcraft, the RF front end comprising multiple Contains multiple different antenna arrays distributed on different rotor blades. As before, the rotorcraft includes a central rotating hub and a plurality of rotor blades connected to the central rotating hub. Further, the method is performed to simultaneously propagate multiple different RF signals to multiple different target endpoints.

[0095] First, method 1100 includes an act (act 1105) in which the RF backend provides multiple different signals to different antenna arrays, each antenna array providing different signals to different target endpoints (act 1105). For example, as shown in FIG. 8B). Stated another way, each antenna array beam is aimed at a corresponding different target endpoint. Additionally, the RF front end may include multiple different types of RF components (e.g., antennas, amplifiers, mixers, etc.), such that multiple different types of RF components are embedded within the rotor blade. .

[0096] This process of providing multiple different signals to the RF front end may be performed using any of the maneuvering techniques described above. Turning briefly to FIG. 11B, this figure further details some of the processes that may be followed to perform act 1105.

[0097] Specifically, FIG. 11B shows an act of compensating for how different signals are provided to the RF front end based on the rotational speed of the antenna elements/arrays embedded in the rotor blades. 1105A). For example, as previously discussed, the phase of the signal may be modified using an n-dimensional analysis/model to modify, or more precisely compensate for, the rotational properties of the element.

[0098] Additionally, FIG. 11B shows an act of electronically steering at least one main lobe/beam of the antenna element/array throughout the rotational phase of the rotor blade (act 1105B). Of course, any type of electronic steering may be used. Additionally, the electronic steering process includes electronically directing the main lobe of the antenna element/array to the receiver throughout the rotational phase. Furthermore, this maneuver may be based on rotational speed compensation.

[0099] Returning to FIG. 11A, the method 1100 includes the act of performing a conversion, at an RF back end or an RF front end, on a plurality of different signals provided to a plurality of different antenna arrays disposed within different rotor blades. (Act 1100) is also included. This conversion involves converting a plurality of different signals from one or more intermediate frequencies to one or more radio frequencies for signals sent to an external receiver (ie, target endpoint). However, for signals received from a transmitter, this conversion may involve converting from radio frequency to intermediate frequency.

[00100] The method 1100 then includes an act of directing each of the plurality of different antenna arrays to a respective main lobe of the converted RF signal to a respective corresponding target endpoint (act 1115). including. These converted signals may be in the form of electromagnetic waves as shown in FIG. Thus, multiple different RF signals are simultaneously propagated to multiple different target endpoints. Additionally, these RF signals are first propagated from the rotor blades of the rotorcraft and then directed into three-dimensional space to different target endpoints.

[00101] Thus, by following the disclosed embodiments, significant technical improvements and effects may be achieved. That is, additional RF communication links may be established without substantially changing the weight of the rotorcraft and without moving other hardware components that need to be installed on the rotorcraft. Furthermore, some of those links can be formed without having to consider the overhead shadow of the rotor blades.

computer system example
[00102] Turning now to FIG. 12, illustrated is an example computer system 1200 that can be used to facilitate the operations described herein. Computer system 1200 may be included in a variety of rotorcraft. For example, in FIG. 12, computer system 1200 may also be included in a helicopter 1200A, a drone 1200B, or a tilt-wing (tiltrotor) aircraft 1200C. Although only three types of rotorcraft are shown, computer system 1200 can be included in any type of rotorcraft. In some implementations, computer system 1200 is included as part of the RF back end of the antenna system.

[00103] In its most basic configuration, computer system 1200 includes various components. For example, FIG. 12 shows that computer system 1200 includes at least one processor 1205 (also known as a "hardware processing unit"), antenna hardware 1210 (e.g., any of the antennas, amplifiers, mixers, tuning units, etc. described above), etc.) and a modem 1215. Modem 1215 includes an antenna beam steering engine 1220, an LPI engine 1225, an LPD engine 1230, an anti-jamming engine 1235, a geolocation engine 1240, a satellite communication engine 1245, a video interface 1250, a network interface 1255, and a modem processor 1260. Computer system 1200 also includes storage 1265.

[00104] As used herein, the terms "executable module," "executable component," "engine," and even the term "component" refer to software objects that may be executed on computer system 1200. It can mean a routine or a method. The different components, modules, engines, and services described herein may be implemented as objects or processors executing on computer system 1200 (eg, as separate threads). An engine, module, or component may be a combination of one or more processors and executable instructions that cause the processor to perform specialized functions, those specialized functions described in this disclosure. , particularly those relating to the individual method acts described in FIGS. 11A and 11B.

[00105] Antenna beam steering engine 1220 may be used to perform any of the disclosed electronic steering techniques (eg, MIMO, OAM, etc.). LPI engine 1225 may be used to perform LPI techniques, and similarly, LPD engine 1230 may be used to perform LPD techniques. Anti-jamming engine 1235 provides anti-jamming, geolocation engine 1240 provides geolocation, and satellite communications engine 1245 provides satellite interference and other types of satellite communications. Video interface 1250 can perform video transmission. Network interface 1255 can be used to communicate with any type of network. Modem processor 1260 can be used to coordinate the activity of these other engines and/or to perform any other operations.

[00106] Storage 1265 may include computer-executable instructions in the form of code 1270. Storage 1265 may be physical system memory, which may be volatile, non-volatile, or some combination of the two. As used herein, the term "memory" may also refer to non-volatile mass storage devices such as physical storage media. If computer system 1200 is distributed, processing, memory, and/or storage capacity may also be distributed.

[00107] In other examples, a component, module, or engine may simply be executable instructions that can be executed by any type of processor. In still other examples, the component, module, or engine may be in the form of an ASIC and configured to perform any discrete operation (e.g., any one of the acts included in the methods of FIGS. 11A and 11B). It may be a system-on-a-chip (“SOC”) device that is specially configured to perform the same or multiple operations (eg, any of the combinations of the method acts of FIGS. 11A and 11B). In this regard, a component, module, or engine may be considered a hardware processing unit, a compilation of executable code, or a combination of the above that can cause a computer system to perform a specialized operation.

[00108] The disclosed embodiments may comprise or utilize a special purpose or general purpose computer that includes computer hardware, such as one or more processors (such as processor 1205) and system memory. (storage 1265, etc.), which will be described in detail below. Embodiments also include physical and other computer-readable media for carrying or storing computer-executable instructions and/or data structures. Such computer-readable media can be any available media that can be accessed by a general purpose or special purpose computer system. Computer-readable media that store computer-executable instructions in the form of data are physical computer storage media. Computer-readable media that carry computer-executable instructions are transmission media. Thus, by way of example and not limitation, current embodiments may include at least two distinctly different types of computer-readable media: computer storage media and transmission media.

[00109] The computer storage medium is a hardware storage device, which includes RAM, ROM, EEPROM, CD-ROM, RAM-based solid state drive (SSD), flash memory, phase change memory (PCM), or any other type of memory, or other optical disk storage, magnetic disk storage, or other magnetic storage device, or for storing desired program code means in the form of computer-executable instructions, data, or data structures. such as any other medium that can be used for computer purposes and accessed by a general purpose or special purpose computer.

[00110] Computer system 1200 may communicate (via wired or wireless communications) to external sensors (e.g., one or more remote cameras, accelerometers, gyroscopes, acoustic sensors, magnetometers, data acquisition systems, etc.). May be connected. Additionally, computer system 1200 may be connected by one or more wired or wireless networks 1275 to remote/separate computer systems configured to perform any of the operations described with respect to computer system 1200. Additionally, computer system 1200 can wirelessly communicate with other computer systems by propagating electromagnetic signals to target endpoints. Although not shown, computer system 1200 may include any number of input/output ("I/O") devices (e.g., a display, keyboard, mouse, etc.) or a device for rendering one or more images to a user. It may also include modules/engines (display graphics and graphics rendering engines) that are configured with the processor 1205.

[00111] A "network," such as network 1275A shown in FIG. 12, refers to one or more data links that enable the transport of electronic data between computer systems, modules, and/or other electronic devices. and/or data switch. When information is sent or provided to a computer over a network (hardwired, wireless, or a combination thereof), the computer formally views the connection as a transmission medium. Computer system 1200 will include one or more communication channels used to communicate with network 1275. Transmission media include networks that can be used to carry data or desired program code means in the form of computer-executable instructions or data structures. Further, these computer-executable instructions can be accessed by a general purpose or special purpose computer. Combinations of the above should also be included within the scope of computer-readable media.

[00112] Program code means in the form of computer-executable instructions or data structures can be automatically transferred from transmission media to computer storage media (and vice versa) upon arrival at various computer system components. For example, computer-executable instructions or data structures received over a network or data link may be buffered in RAM within a network interface module (e.g., a network interface card, or "NIC") before ultimately being sent to the computer system. The data may be transferred to computer system RAM and/or to less volatile computer storage media. Accordingly, it should be understood that computer storage media can be included in computer system components that also (or primarily) utilize transmission media.

[00113] It will be appreciated that computer-executable (or computer-interpretable) instructions comprise, for example, instructions that cause a general purpose computer, special purpose computer, or special purpose processing device to perform a particular function or group of functions. Computer-executable instructions may be, for example, binaries, intermediate format instructions such as assembly language, or source code. Although the subject matter has been described in terms specific to structural features and/or methodological acts, it is to be understood that the subject matter defined in the appended claims is not limited to the features and acts described above. . Rather, the described features and acts are disclosed as example forms of implementing the claims.

[00114] Embodiments apply to personal computers, desktop computers, laptop computers, message processors, handheld devices, multiprocessor systems, microprocessor-equipped or programmable consumer electronics, network PCs, minicomputers, main Those skilled in the art will appreciate that the present invention may be implemented in many types of computer system configurations, including frame computers, cell phones, PDAs, pagers, routers, switches, and the like. Embodiments also provide that local or remote computer systems linked through a network (by hardwired data links, wireless data links, or a combination of both) each perform tasks (e.g., cloud computing, cloud services, etc.). may be implemented in a distributed systems environment. In a distributed system environment, program modules may be located in both local and remote memory storage devices.

[00115] Additionally and alternatively, the functions described herein can be performed, at least in part, by one or more hardware logic circuit components (eg, processor 1205). For example, and without limitation, examples of the types of hardware logic circuit components that may be used include field programmable gate arrays (PGAs), program specific or application specific integrated circuits (ASICs), program specific standard products (ASSPs), Includes systems on a chip (SOC), complex programmable logic devices (CPLDs), central processing units (CPUs), and other types of programmable hardware. The disclosed embodiments also support waveform generation and modem functionality.

[00116] The present invention may be embodied in other specific forms without departing from the spirit or characteristics thereof. The described embodiments are in all respects illustrative only and not restrictive. The scope of the invention is, therefore, indicated by the appended claims rather than by the foregoing description. All changes that come within the meaning and range of equivalency of the claims are to be embraced within their scope. Furthermore, any disclosed feature, process, principle, or act may be implemented individually or in combination with any other disclosed principles.

Claims (19)

1. An antenna system for facilitating narrowband and wideband radio frequency (RF) communications for a rotorcraft, the rotorcraft comprising a first central rotating hub and a plurality of rotorcraft connected to the first central rotating hub. a second rotating hub and a plurality of secondary rotor blades connected to the second rotating hub, the antenna system comprising:
An RF front end that includes a plurality of RF components configured to transmit and receive RF communications as electromagnetic waves into a three-dimensional space, the RF front end comprising:
the plurality of RF components forming part of at least one of the rotor blades and at least one of the secondary rotor blades;
an RF front end, wherein at least some of the plurality of RF components are of different types, such that the at least one rotor blade and the at least one secondary rotor blade include a plurality of different types of RF components; ,
an RF back end connected to the RF front end via the central rotating hub;
Equipped with
the different types of RF components are embedded in an inner portion of the at least one rotor blade and the at least one secondary rotor blade;
the at least one rotor blade and the at least one secondary rotor blade include at least one antenna array and at least one RF amplifier;
the RF front end is configured to provide RF communication link diversity, the RF communication link comprising a first communication link using the RF component of the at least one rotor blade; a second communication link using the RF component of a secondary rotor blade of the antenna system. The antenna system of claim 1, wherein the plurality of RF components are embedded in an inner portion of the at least one rotor blade such that the plurality of RF components are not exposed to an external environment. 2. The antenna system of claim 1, wherein the plurality of RF components are configured to establish multiple communication links simultaneously. The antenna system according to claim 1,
a first set of RF components of the plurality of RF components are physically located near a backside of the at least one rotor blade;
a second set of RF components of the plurality of RF components are physically located near the ventral surface of the at least one rotor blade;
the ventral surface is an opposite surface with respect to the dorsal surface;
antenna system. The antenna system according to claim 4,
the first set of RF components located near the dorsal surface are controlled simultaneously and independently of the second set of RF components located near the ventral surface;
The first set of RF components transmits or receives a first electromagnetic wave in an upward direction with respect to the rotorcraft, and simultaneously the second set of RF components transmits or receives a second electromagnetic wave in a downward direction with respect to the rotorcraft. transmit or receive electromagnetic waves,
antenna system. The antenna system according to claim 1 ,
An antenna system , wherein each antenna array comprises one or more corresponding antenna elements. 7. The antenna system according to claim 6,
The different types of RF components embedded in the at least one rotor blade include one or more mixers configured to convert an RF signal to an intermediate frequency (IF) signal or an IF signal to an RF signal. further including;
the one or more antenna arrays embedded in the inner portion of the at least one rotor blade;
tapered vivaldi antenna array,
comprising one or more of a staggered patch antenna array, or a linear circularly polarized antenna array;
antenna system. 7. The antenna system of claim 6, wherein each of the one or more antenna elements embedded in the inner portion of the at least one rotor blade is independently operable as an independent antenna unit. An antenna system, wherein each of the one or more antenna elements is independently signaled. 7. The antenna system according to claim 6,
the one or more antenna elements embedded in the inner portion of the at least one rotor blade includes a plurality of antenna elements;
the plurality of antenna elements are collectively controllable via electronic antenna steering such that the plurality of antenna elements are collectively operable as an antenna unit;
antenna system. A communication system for facilitating radio frequency (RF) communications in a rotorcraft, the RF communications comprising narrowband and/or wideband signals, the rotorcraft having a central rotating hub and a central rotating hub. a plurality of rotor blades connected to the communication system;
An RF front end including a plurality of antenna arrays and a plurality of amplifiers, the RF front end comprising:
Each antenna array of the plurality of antenna arrays includes a plurality of antenna elements,
a first set of antenna elements and amplifiers embedded in an inner portion of a first rotor blade included in the plurality of rotor blades;
a second set of antenna elements and amplifiers embedded in an inner portion of a second rotor blade included in the plurality of rotor blades;
RF front end and
an RF back end connected to the RF front end via the centrally rotating hub, the RF back end at least converting a digital signal to an analog signal or converting an analog signal to a digital signal and providing diversity in an RF communication link; and the RF communication link includes a first communication link using the first rotor blade and a second communication link using the second rotor blade.
RF backend and
communication system with. 11. The communication system of claim 10, wherein at least some antenna elements included in the first set of antenna elements and amplifiers are shaped to at least partially match the shape of the first rotor blade. communication system. The communication system according to claim 10,
the RF front end including a first set of the antenna element and amplifier embedded in the first rotor blade and a second set of the antenna element and amplifier embedded in the second rotor blade; The RF backend is
low detectability (LPD) of said RF communications;
low probability of interception (LPI) of said RF communications;
anti-jamming of the RF communications; or geolocation of the RF communications;
Communications system. The communication system according to claim 10,
the RF front end including a first set of the antenna element and amplifier embedded in the first rotor blade and a second set of the antenna element and amplifier embedded in the second rotor blade; an RF backend configured together to send or receive the RF communications;
The RF communication spans one or more of the L band, S band, C band, Ku band, Ka band, or a band higher than 40 GHz up to 90 GHz.
Communications system. The communication system according to claim 10,
the plurality of antenna arrays include a broadband antenna array;
the wideband antenna array is configured to provide satellite interference mitigation with one or more sidelobes of an antenna pattern of the wideband antenna array;
Communications system. A method for simultaneously propagating a plurality of different radio frequency (RF) signals to a plurality of different target endpoints, the plurality of different RF signals being propagated by a plurality of different antenna arrays included in an RF front end of an antenna system. the antenna system also includes an RF backend, the antenna system is included as part of a rotorcraft, the rotorcraft having a central rotating hub and a plurality of rotor blades connected to the central rotating hub. wherein the plurality of rotor blades include a plurality of RF components of different types, the method comprising:
causing the RF backend to simultaneously provide a plurality of different signals to different antenna arrays, each embedded in a different one of the rotor blades of the rotary-wing aircraft; each aimed at a corresponding different target endpoint to provide RF communication link diversity by the different target endpoints of the different antenna arrays, the RF communication link being aimed at at least one of the rotor blades. a first communication link using an RF component; and a first communication link using an RF component of the at least one secondary rotor blade.
step and
converting the plurality of different signals from one or more intermediate frequencies to one or more radio frequencies at either the RF back end or the RF front end;
directing each of the different antenna arrays to a corresponding converted RF signal to a corresponding target endpoint, such that a plurality of different RF signals simultaneously propagate to a plurality of different target endpoints; , causing the plurality of RF signals to initially propagate from the rotor blade of the rotorcraft to the plurality of different target endpoints. 16. The method according to claim 15,
The method further comprising electronically steering each of the different antenna arrays independently of each other. 16. The method of claim 15, wherein the plurality of different RF signals include both audio and video signals. 16. The method of claim 15, wherein the rotorcraft is a helicopter, a drone, or a tiltrotor aircraft. 16. The method according to claim 15,
performing compensation with the plurality of different signals, the compensation being based on rotational speeds of the different antenna arrays;
electronically steering the different antenna arrays through multiple full rotational phases of the rotor blade;
Further comprising a method.

Images